FIELD: turbines or turbomachines.
SUBSTANCE: described is a method of diagnosing faults during testing of a turbine installation in a turbine testing system, wherein the turbine plant comprises a plurality of turbine components and turbine sensors, and the turbine test system comprises a plurality of test sensors. Described method comprises steps of: (a) obtaining measurement data from turbine sensors and test sensors, (b) calculating at least one parameter value based on measurement data, (c) determining deviation of measurement data and at least one parameter value by comparing measurement data and at least one parameter value with given control data and (d) comparing a certain deviation with a plurality of predetermined fault signatures for fault detection, wherein a plurality of predetermined fault signatures comprises a first set of fault signatures and a second set of fault signatures, wherein the first set of fault signatures corresponds to faults of turbine sensors and/or faults of test sensors and assumed working components of turbine, and the second set of fault signatures corresponds to faults of turbine components and to supposed serviceable turbine sensors and test sensors.
EFFECT: this method provides the possibility of distinguishing faults that can be immediately eliminated, and faults that require additional inspection or repair of the turbine plant.
11 cl, 11 dwg
Title | Year | Author | Number |
---|---|---|---|
TROUBLE-SHOOTING SYSTEM FOR ELECTRIC MOTORS BASED ON MODEL | 1997 |
|
RU2155328C1 |
SYSTEM AND DEVICE FOR MONITORING OF TURBOJET ENGINE VARIABLE GEOMETRY ACTUATOR SYSTEM FEEDBACK LOOP | 2011 |
|
RU2580194C2 |
DIAGNOSTICS OF DIESEL EXHAUST GAS CIRCULATION (EGR) COOLANT | 2010 |
|
RU2544682C2 |
METHOD FOR DIAGNOSING REDUNDANT MEASUREMENT CHANNELS (VERSIONS) | 2019 |
|
RU2705169C1 |
METHOD FOR DIAGNOSING THE TECHNICAL CONDITION OF GAS TURBINE ENGINES BASED ON THERMOGASDYNAMIC PARAMETERS IN TRANSIENT AND STEADY-STATE MODES (FROM IDLE RUN TO RATED POWER MODE) APPLYING THE INVARIANT THEORY | 2021 |
|
RU2774092C1 |
DETECTION AND ADAPTATION TO INTERMITTENT CIRCUIT BREAKING ON SENSOR OF AVIATION TURBINE ENGINE | 2018 |
|
RU2784316C2 |
METHOD AND SYSTEM FOR ADVISING OPERATOR ACTION | 2013 |
|
RU2657047C2 |
METHOD AND SYSTEM FOR RULES OF POWERFUL GAS TURBINES DIAGNOSTICS | 2013 |
|
RU2613637C2 |
METHOD OF AIRCRAFT AND HELICOPTER DIAGNOSTICS AND REPAIR | 2010 |
|
RU2423296C1 |
METHOD OF CHECKING AND DIAGNOSING PNEUMOHYDRAULIC OBJECT CONDITION | 1998 |
|
RU2133952C1 |
Authors
Dates
2019-07-09—Published
2017-04-21—Filed